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Production of UO₃ by Calcination of Uranyl Peroxide

Description: This report discusses the calcination or heating of UO₃. When UO₃ is heated, it loses ionic impurities and can produce uranyl peroxide.
Date: December 10, 1952
Creator: Moore, R. L. & Watts, R. A., Jr.
Partner: UNT Libraries Government Documents Department
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Liquid-Liquid Dispersions and the Significance of the Disengaging Test

Description: From introduction: "The purpose of this report is to summarize some of the observations on the dispersion and rate of disengaging of liquid-liquid systems and suggest some possible lines of future work."
Date: July 10, 1952
Creator: Burger, L. L.; Dillon, R. L. & Johnson, W. F.
Partner: UNT Libraries Government Documents Department
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Graphite surface studies

Description: This report discusses the the surface characteristics of virgin and irradiated artificial graphites and the changes which occur upon irradiation.
Date: October 10, 1952
Creator: Spalaris, C. N.
Partner: UNT Libraries Government Documents Department
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Geology of Horse Mesa, Arizona - New Mexico, with Recommendations for Wagon Drilling

Description: Abstract: Horse Mesa is in the Navajo Indian Reservation directly on the Arizona-New Mexico state line. Uranium-vanadium deposits in the Salt Wash sandstone which caps the Mesa are fairly widespread and small tonngges have been shipped from two mines. The deposits lie 60 to 75 feet above the base of the Salt Wash formation and possibly trend northwest parallel to ore trends on King Tutt Mesa, a mile northeast. Carnotite and vanoxite are the principal ore minerals. About 6,000 feet of wagon dril… more
Date: September 10, 1952
Creator: King, John W.
Partner: UNT Libraries Government Documents Department
open access

A Vapor Pressure Chart for Metals

Description: From conclusions: There is a close enough correlation for most metals to give the chart some utility in estimating vapor pressure of metals.
Date: July 10, 1952
Creator: Loftness, Robert L.
Partner: UNT Libraries Government Documents Department
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The Densities of Uranyl Sulfate Solutions Between 20° and 90°C

Description: The densiies of uranyl sulfate water solutions were measure or 12 concentrations between the temperatures of 20° and 90°C. The density range at 20°C is 1.0539 grams per cubic centimeter at 0.17 molal to 2.0059 grams per cubic centimeter at 3.9 molal.
Date: October 10, 1952
Creator: Jegart, J.S.; Heiks, J.R. & Orban, E.
Partner: UNT Libraries Government Documents Department
open access

First Quarterly Report on the Reductions of Uranium Oxides

Description: The preliminary results of a program designed to evaluate methods for preparing uranium hydride from the various oxides of uranium are presented. The apparatus has been designed and constructed for the purpose of carrying out batch reductions under a variety of conditions employing calcium hydride, calcium metal and magnesium metal as the reducing agents. Since the separation of the alkaline earth oxides, present as by-products in the furnace products, promises to be the most difficult problem … more
Date: October 10, 1952
Creator: Bragdon, R. W.
Partner: UNT Libraries Government Documents Department
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Some Aspects of Reactor Theory

Description: Report that outlines the major issue of reactor theory and asymptotic reactor theory. Uncommon reactor theory results are also discussed and unanswered questions regarding reactor theory are presented by the author.
Date: October 10, 1952
Creator: Weinberg, Alvin Martin, 1915-2006
Partner: UNT Libraries Government Documents Department
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234-5 Building RM line equipment tests, Task III mixer

Description: Several operations that are important to the process as carried out in Task III (Reduction) are performed by the mixer. In order to specify the process certain tests were made to study these operations and are discussed in this report. They include: Mixing Time, Mixer Discharge Rate, Mixer Holdup, and Mixer Capacity. A description of the test, conclusions and recommendations is provided.
Date: April 10, 1952
Creator: Collins, P. E.
Partner: UNT Libraries Government Documents Department
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Impingement of water droplets on an NACA 65(sub 1) -212 airfoil at an angle of attack of 4 degrees

Description: The trajectories of droplets in the air flowing past an NACA 651-212 airfoil at an angle of attack of 40 were determined. The collection efficiency, the area of droplet impingement, and the rate of droplet impingement were calculated from the trajectories and are presented herein.
Date: September 10, 1952
Creator: Brun, Rinaldo J.; Serafini, John S. & Moshos, George J.
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of control characteristics at transonic speeds of a tapered 45 degree sweptback wing of aspect ratio 3 having a horn-balanced full-span control

Description: Report presenting an investigation at transonic speeds in the 7- by 10-foot tunnel to determine hinge-moment and effectiveness characteristics of a horn-balanced control on an aspect-ratio-3, 45 degree sweptback wing. The investigation was extended through the transonic speed range by testing in the high velocity field over a reflection plane on the sidewall of the tunnel.
Date: April 10, 1952
Creator: Lowry, John G. & Fikes, Joseph E.
Partner: UNT Libraries Government Documents Department
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Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Twisted and cambered triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution

Description: Report presenting the results of a wind-tunnel investigation at subsonic and supersonic Mach numbers to determine the aerodynamic characteristics of a wing-body combination with a triangular wing of aspect ratio 2. The mean surface of the wing was twisted and cambered to support a nearly elliptical span load distribution at Mach number 1.53 and a lift coefficient of 0.25. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date: April 10, 1952
Creator: Heitmeyer, John C. & Petersen, Robert B.
Partner: UNT Libraries Government Documents Department
open access

Component and over-all performance evaluation of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers

Description: Report presenting an investigation in an altitude test chamber to evaluate the performance of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers. Reducing the engine inlet Reynolds number resulted in a reduction of corrected air flow and compressor efficiency but did not affect the compressor pressure ratio at a given corrected engine speed.
Date: July 10, 1952
Creator: Walker, Curtis L.; Huntley, S. C. & Braithwaite, W. M.
Partner: UNT Libraries Government Documents Department
open access

Investigation at Mach Number 2.93 of Half of a Conical-Spike Diffuser Mounted as a Side Inlet With Boundary-Layer Control

Description: Report presenting an investigation to determine the performance characteristics of a side inlet with boundary-layer control operating in the presence of laminar and turbulent initial boundary layers at a free-stream Mach number of 2.93. Results regarding mass-flow and total-pressure referencing, visual-flow observations, inlet performance, and boundary-layer-scoop performance are provided.
Date: September 10, 1952
Creator: Piercy, Thomas G. & Johnson, Harry W.
Partner: UNT Libraries Government Documents Department
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Altitude investigation of three flame-holder and fuel-systems configurations in a short converging afterburner on a turbojet engine

Description: From Introduction: "Previous investigations of a number of internal configurations in the same afterburner shell are reported in reference 1 and 2. In the investigation reported herein, the performance and operational characteristics of three afterburner internal configurations were evaluated."
Date: September 10, 1952
Creator: Braithwaite, Willis M.; Renas, Paul E. & Jansen, Emmert T.
Partner: UNT Libraries Government Documents Department
open access

Effect of trailing edge thickness on lift at supersonic velocities

Description: Report presenting measurements of lift made on various rectangular-plan-form wings differing in trailing-edge thickness, profile shape, maximum thickness ratio, and aspect ratio. Experiments were conducted at a range of Mach numbers, Reynolds numbers, and wings with and without boundary-layer trips. Results regarding a comparison of experimental results with theory at moderate supersonic Mach numbers and calculations for hypersonic Mach numbers are provided.
Date: July 10, 1952
Creator: Chapman, Dean R. & Kester, Robert H.
Partner: UNT Libraries Government Documents Department
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Investigation of vanes immersed in the jet of a solid-fuel rocket motor

Description: Report presenting a determination of the characteristics of a particular vane configuration in the jet of a 6.25-inch Deacon solid-fuel rocket motor from static testing. The vanes were oscillated during the test to provide comprehensive data over a range of deflection angles. The effects of the rocket jet on two vane materials, the aerodynamic characteristics of the vanes, and the influence of jet vanes on rocket-motor performance were determined.
Date: September 10, 1952
Creator: Giladett, Leo V. & Wineman, Andrew R.
Partner: UNT Libraries Government Documents Department
open access

Survey of some preliminary investigations of supersonic diffusers at high Mach numbers

Description: From Introduction: "Design studies of long-range supersonic missiles indicate the Mach number range of 3 to 4 to be of considerable promise. Accordingly, the NACA is conducting research on the performance of a wide variety of supersonic diffusers in this range. The initial phase of this research is concerned primarily with the characteristics of conventional axially symmetric diffusers operating at design values of flight Mach number."
Date: July 10, 1952
Creator: Cortright, Edgar M., Jr. & Connors, James F.
Partner: UNT Libraries Government Documents Department
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Solubility of water in hydrocarbons

Description: Report presenting a study of the literature data on the solubility of water in hydrocarbons, which includes information about the log of solubility, critical solution temperature, and ratios that may affect solubility are provided. An equation is presented and applied to a few petroleum fractions ranging from gasoline to lubricating oil, and a comparison of calculated and experimental solubilities is provided.
Date: July 10, 1952
Creator: Hibbard, R. R. & Schalla, R. L.
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Lateral-Control Investigation of a Flap-Type Spoiler Aileron With and Without a Deflector and Slot on a 6-Percent-Thick, Tapered, 45 Degree Sweptback Wing of Aspect Ratio 4

Description: Memorandum presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the lateral control characteristics of a deflector and slot arrangement in conjunction with a flap-type spoiler aileron. The wing had a sweepback of 45 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free air stream.
Date: September 10, 1952
Creator: Watson, James M.
Partner: UNT Libraries Government Documents Department
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An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degrees Sweepback: Estimated Downwash Angles Derived From Pressure Measurements on the Tail at Mach Numbers of 1.40 and 1.59

Description: Report presenting estimates of downwash angles determined from an analysis of pressures measured on the horizontal tail of a supersonic aircraft configuration. The results are compared to an approximate application of linearized theory and force-test results for the same configuration.
Date: March 10, 1952
Creator: Grant, Frederick C. & Gapcynski, John P.
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of an axial flow compressor inlet stage operating at transonic relative inlet Mach numbers 1: over-all performance of stage with transonic rotor and subsonic stators up to rotor relative inlet Mach number of 1.1

Description: Report presenting the design, construction, and investigation of an axial-flow compressor inlet stage with a maximum rotor relative inlet Mach number of 1.1. The rotor was designed for a high axial inlet velocity, no inlet guide vanes, and a tip speed of 1000 feet per second. Results regarding the overall performance, rotor inlet conditions, and stator exit conditions are provided.
Date: March 10, 1952
Creator: Lieblein, Seymour; Lewis, George W., Jr. & Sandercock, Donald M.
Partner: UNT Libraries Government Documents Department
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